In this chapter, we demonstrate the applicability of the standard linear quadratic regulator (LQR) and state-dependent Riccati Equation (SDRE) based on linear and nonlinear optimal controllers to achieve the objective of satellite formation flying. Infinite-time formulations of LQR and SDRE offer the advantage of simplicity naturally and hence they are widely preferred in various applications. The utility of these methods for satellite formation flying is demonstrated in their respective validity regions. Both methods are effective when the chief satellite is in the circular orbit and the relative separation distance is small. On the other hand, the SDRE-based formulation is found to be effective even for eccentric orbits, but only with small eccentricity.
Infinite-Time LQR and SDRE for Satellite Formation Flying
Satellite Formation Flying ; Kapitel : 3 ; 45-65
2021-03-16
21 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
Finite-Time LQR and SDRE for Satellite Formation Flying
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